Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 /Rules and Regulations 36551

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

98–14–10 Boeing: Amendment 39–10643.

Docket 98–NM–155–AD.

Applicability: Model 747–400, 757, 767,

and 777 series airplanes; equipped with

AlliedSignal RIA–35B Instrument Landing

System (ILS) receivers, part number (P/N)

066–50006–0101; certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (e) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To detect and correct faulty ILS receivers,

and to ensure that the flightcrew is advised

of the potential hazard of performing ILS

approaches using a localizer deviation from

a faulty ILS receiver and also advised of the

procedures necessary to address that hazard,

accomplish the following:

(a) Within 10 days after the effective date

of this AD, revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) to include the following statement.

This may be accomplished by inserting a

copy of this AD into the AFM.

Any Instrument Landing System (ILS) or

Localizer approach with only one operative

AlliedSignal ILS receiver, P/N 066–50006–

0101, installed is prohibited.

Note 2: On Model 747–400 and 777 series

airplanes, the existence of only one operative

ILS receiver is indicated by the Engine

Indication and Crew Alerting System

advisory message, ‘‘SNGL SOURCE ILS.’’ On

Model 757 and 767 series airplanes, failure

of an ILS receiver is indicated by an ILS flag

on the display of the Electronic Flight

Instrument System when approach mode is

selected.

(b) Within 30 days after the effective date

of this AD, accomplish the requirements of

either paragraph (b)(1) or (b)(2) of this AD.

(1) Perform a visual inspection of the 64

flight legs of the internal fault memory of all

AlliedSignal RIA–35B ILS receivers, P/N

066–50006–0101, for fault codes ‘‘Nl’’ (glide

slope antialias fault) or ‘‘Nm’’ (localizer

antialias fault). Repeat the inspection

thereafter at intervals not to exceed 64 flight

cycles. If any fault code ‘‘Nl’’ or ‘‘Nm’’ is

found, prior to further flight, replace the

existing ILS receiver with a new or

serviceable ILS receiver having the same P/

N; or with an ILS receiver that has been

modified to P/N 066–50006–1101 in

accordance with AlliedSignal Electronic and

Avionics Systems Service Bulletin M–4426

(RIA–35B–34–6), Revision 3, dated May

1998. Installation of an ILS receiver that has

been modified (and the P/N converted) in

accordance with the service bulletin

constitutes terminating action for the

inspection requirement of paragraph (b)(1) of

this AD for that part.

(2) Accomplish the actions required by

paragraphs (b)(2)(i) and (b)(2)(ii) of this AD.

(i) Revise the Limitations Section of the

FAA-approved AFM to include the following

statement. This may be accomplished by

inserting a copy of this AD into the AFM.

Category II and III operations are

prohibited with AlliedSignal ILS receiver P/

N 066–50006–0101 installed.

(ii) Install a placard on the forward

instrument panel of the cockpit in clear view

of the pilots, which states:

‘‘Category II and III operations are

prohibited.’’

(c) Replacement of all existing RIA–35B

ILS receivers, P/N 066–50006–0101, with

RIA–35B ILS receivers that have been

modified in accordance with AlliedSignal

Electronic and Avionics Systems Service

Bulletin M–4426 (RIA–35B–34–6), Revision

3, dated May 1998; and that have had their

P/N’s converted to 066–50006–1101;

constitutes terminating action for the

requirements of this AD. After the

replacement has been accomplished, the

AFM limitations required by paragraphs (a)

and (b)(2)(i) of this AD may be removed from

the AFM, and the placard required by

(b)(2)(ii) may be removed from the cockpit.

Note 3: Modification of all AlliedSignal

RIA–35B ILS receivers, P/N 066–50006–0101,

prior to the effective date of this AD in

accordance with AlliedSignal Electronic and

Avionics Systems Service Bulletin M–4426

(RIA–35B–34–6), dated December 1997;

Revision 1, dated January 1998; or Revision

2, dated April 1998; is considered acceptable

for compliance with the applicable action

specified in this amendment.

(d) As of the effective date of this AD, no

person shall install on any airplane an RIA–

35B ILS receiver, P/N 066–50006–0101, that

has been found to be discrepant (that is, on

which fault codes ‘‘Nl’’ or ‘‘Nm’’ were found

during an inspection of the internal fault

memory) unless the discrepancy has been

corrected by modifying the ILS receiver in

accordance with AlliedSignal Electronic and

Avionics Systems Service Bulletin M–4426

(RIA–35B–34–6), Revision 3, dated May

1998.

(e) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Seattle ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(f) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the airplane to a

location where the requirements of this AD

can be accomplished.

(g) The modification, if accomplished,

shall be done in accordance with

AlliedSignal Electronic and Avionics

Systems Service Bulletin M–4426 (RIA–35B–

34–6), Revision 3, dated May 1998. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from

AlliedSignal Aerospace, Technical

Publications, Dept. 65–70, P.O. Box 52170,

Phoenix, Arizona 85072–2170. Copies may

be inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(h) This amendment becomes effective on

July 22, 1998.

Issued in Renton, Washington, on June 29,

1998.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17914 Filed 7–6–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–139–AD; Amendment

39–10648; AD 98–14–15]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F27 Mark 100, 200, 300, 400, 500,

600, and 700 Series Airplanes, and

Model F27 Mark 050 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.
36552 Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 /Rules and Regulations

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Fokker Model F27

Mark 100, 200, 300, 400, 500, 600, and

700 series airplanes, and Model F27

Mark 050 series airplanes, that requires

revising the Airplane Flight Manual to

modify the limitation that prohibits

positioning the power levers below the

flight idle stop during flight, and to

provide a statement of the consequences

of positioning the power levers below

the flight idle stop during flight. This

amendment is prompted by incidents

and accidents involving airplanes

equipped with turboprop engines in

which the ground propeller beta range

was used improperly during flight. The

actions specified by this AD are

intended to prevent loss of airplane

controllability caused by the power

levers being positioned below the flight

idle stop while the airplane is in flight.

EFFECTIVE DATE: Effective August 11,

1998.

ADDRESSES: Information pertaining to

this rulemaking action may be examined

at the Federal Aviation Administration

(FAA), Transport Airplane Directorate,

Rules Docket, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Mark Quam, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue SW., Renton,

Washington 98055–4056; telephone

(425) 227–2145; fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Fokker Model

F27 Mark 100, 200, 300, 400, 500, 600,

and 700 series airplanes, and Model F27

Mark 050 series airplanes, was

published in the Federal Register on

March 20, 1998 (63 FR 13569). That

action proposed to require revising the

FAA-approved Airplane Flight Manual

to modify the limitation that prohibits

positioning the power levers below the

flight idle stop during flight, and to

provide a statement of the consequences

of positioning the power levers below

the flight idle stop during flight.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

Request to Install Automatic Flight Idle

Stop Mechanical System

The commenter supports the

proposed rule, but remarks that, as an

added measure of safety, the FAA

should consider the addition of a

mechanical means to preclude such

selection. The mechanical means

referenced by the commenter would be

in the form of an automatic flight idle

stop. The FAA acknowledges the

commenter’s concern, and may consider

additional rulemaking to address that

concern in the future on certain

airplanes. However, until such final

action is identified, the FAA considers

it appropriate to proceed with issuance

of this final rule. No change to the final

rule is required.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Interim Action

This is considered interim action

until final action is identified, at which

time the FAA may consider further

rulemaking.

Cost Impact

The FAA estimates that 49 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $2,940, or $60 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects on the

States, on the relationship between the

national government and the States, or

on the distribution of power and

responsibilities among the various

levels of government. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

98–14–15 Fokker Services B.V.:

Amendment 39–10648. Docket 97–NM–139–

AD.

Applicability: All Model F27 Mark 100,

200, 300, 400, 500, 600, and 700 series

airplanes, and Model F27 Mark 050 series

airplanes; certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (b) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent loss of airplane controllability

caused by the power levers being positioned

below the flight idle stop while the airplane

is in flight, accomplish the following:

(a) Within 30 days after the effective date

of this AD, revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) to include the following statements as

specified in paragraph (a)(1) or (a)(2) of this

AD, as applicable. This action may be

accomplished by inserting a copy of this AD

into the AFM.

(1) For Model F27 Mark 100, 200, 300, 400,

500, 600, and 700 series airplanes, insert the

following:

‘‘Warning: Ground fine pitch must not be

selected in flight. This may lead to loss of
Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 /Rules and Regulations 36553

control from which recovery may not be

possible.’’

(2) For Model F27 Mark 050 series

airplanes, insert the following:

‘‘Warning: Do not attempt to select ground

idle in flight. In case of failure of the flight

idle stop, this would lead to loss of control

from which recovery may not be possible.’’

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(c) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(d) This amendment becomes effective on

August 11, 1998.

Issued in Renton, Washington, on June 30,

1998.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17948 Filed 7–6–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–72–AD; Amendment

39–10647; AD 98–14–14]

RIN 2120–AA64

Airworthiness Directives;

Turbopropeller-Powered McDonnell

Douglas Model DC–3 and DC–3C

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model DC–3 and DC–3C series

airplanes, that requires revising the

Airplane Flight Manual (AFM) to

modify the limitation that prohibits

positioning the power levers below the

flight idle stop during flight, and to

provide a statement of the consequences

of positioning the power levers below

the flight idle stop during flight. This

amendment is prompted by incidents

and accidents involving airplanes

equipped with turboprop engines in

which the ground propeller beta range

was used improperly during flight. The

actions specified by this AD are

intended to prevent loss of airplane

controllability, or engine overspeed and

consequent loss of engine power caused

by the power levers being positioned

below the flight idle stop while the

airplane is in flight.

EFFECTIVE DATE: August 11, 1998.

ADDRESSES: Information pertaining to

this amendment may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California.

FOR FURTHER INFORMATION CONTACT:

Frank Hoerman, Aerospace Engineer,

Flight Test Branch, ANM–160L, FAA,

Los Angeles Aircraft Certification

Office, 3960 Paramount Boulevard,

Lakewood, California 90712; telephone

(562) 527–5371; fax (562) 625–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain McDonnell

Douglas Model DC–3 and DC–3C series

airplanes was published in the Federal

Register on January 8, 1998 (63 FR

1072). That action proposed to require

revising the Limitations Section of the

Airplane Flight Manual (AFM) to

prohibit the positioning of the power

levers below the flight idle stop while

the airplane is in flight, and to add a

statement of the consequences of

positioning the power levers below the

flight idle stop while the airplane is in

flight.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Interim Action

This is considered interim action

until final action is identified, at which

time the FAA may consider further

rulemaking.

Cost Impact

There are approximately 21

turbopropeller-powered McDonnell

Douglas Model DC–3 and DC–3C series

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

5 airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 1 work hour per airplane

to accomplish the required actions, and

that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the AD on U.S. operators

is estimated to be $300, or $60 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects on the

States, on the relationship between the

national government and the States, or

on the distribution of power and

responsibilities among the various

levels of government. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows: